CN205652347U - Cooling type unmanned aerial vehicle - Google Patents
Cooling type unmanned aerial vehicle Download PDFInfo
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- CN205652347U CN205652347U CN201620283256.2U CN201620283256U CN205652347U CN 205652347 U CN205652347 U CN 205652347U CN 201620283256 U CN201620283256 U CN 201620283256U CN 205652347 U CN205652347 U CN 205652347U
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- fuselage
- drive link
- bar
- cooling type
- type unmanned
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Abstract
The utility model discloses a cooling type unmanned aerial vehicle, including fuselage, main rotor, the tailspin wing, steering wheel, engine and reducing gear box, the reducing gear box with the engine is connected, cooling type unmanned aerial vehicle still includes: the supporting component, the supporting component sets up in the fuselage, the thrust mechanism of amplification, the thrust mechanism of amplification with the steering wheel is connected, cooling device, cooling device with the reducing gear box is connected, a fixing device, the fixing device cover is established on the tail transmission shaft, and with fuselage fixed connection. The not good technical defect of the inside radiating effect of unmanned helicopter fuselage among the prior art has been solved in this application.
Description
Technical field
This utility model relates to unmanned air vehicle technique field, particularly to cooling type unmanned plane.
Background technology
UAV is called for short " unmanned plane ", is to utilize radio robot and the program provided for oneself
Control the most manned aircraft that device is handled.Without driving cabin on machine, but automatic pilot, program are installed
Control the equipment such as device, signal pickup assembly.On ground, naval vessels or machine tool remote control station personnel pass through thunder
The equipment such as reach, it be tracked, position, remote control, remote measurement and Digital Transmission.Can be distant at radio
Take off as conventional airplane under control or launch with booster rocket, it is possible to being taken to aerial throwing by machine tool
Let row fly away.
In prior art, the fuselage interior for unmanned plane cools down, and is the most all the Local cooling used,
By adding gear oil, and the gear-box surface of reduction box in depopulated helicopter is relied on to dispel the heat, but
The heat radiation of this type of cooling is slow, and can only dissipate the surface of the local of unmanned plane such as reduction box
Heat, can not obtain good radiating effect.
Utility model content
This utility model provides a kind of cooling type unmanned plane, solves depopulated helicopter machine in prior art
The technological deficiency that body internal heat dissipating effect is bad.
For solving above-mentioned technical problem, this utility model provides a kind of cooling type unmanned plane, including machine
Body, main rotor, tail rotor, steering wheel, electromotor and reduction box, described reduction box and described electromotor
Connecting, wherein, described main rotor is rotatably fixed with described fuselage by final drive shaft and is connected；Institute
State tail rotor and be fixedly installed on the afterbody of described fuselage, and rotatable with described fuselage by tail transmission shaft
Fix connection；Described electromotor is connected with described main rotor and described tail rotor, is used for driving described
Main rotor and described tail rotor rotate, and described steering wheel is fixed on the inside of described fuselage；Described cooling type
Unmanned plane also includes: support component, and described support component is arranged in described fuselage, for supporting and
Fixing described final drive shaft；Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel,
To amplify the thrust that described steering wheel produces；Chiller, described chiller is connected with described reduction box；
Fixing device, described fixing device is set on described tail transmission shaft, and fixing with described fuselage is connected,
So that described tail transmission shaft and described fuselage are relatively fixed.
Optionally, described support component includes: the first bar；Second bar；And positioning seat；Wherein, institute
State one end of the first bar to be removably secured with described final drive shaft and be connected, the other end of described first bar
Offer a groove；One end of described second bar is set in described groove, one end of described second bar
End and described groove inwall in, put and be provided with one or more elastic ball so that described first bar
And the stress between described second bar is buffered；The other end of described second bar and described positioning seat
One end is rotationally connected so that described second bar is rotatable relative to described positioning seat.
It is optional: the other end of described positioning seat is fixed on described fuselage by a resilient sleeve flexibility,
So that described positioning seat flexibly connects with described fuselage.
Optionally, described thrust amplifying mechanism includes: the first drive link, the one of described first drive link
End is fixed on described fuselage；Second drive link, described machine is fixed in one end of described second drive link
On steering wheel within body；And driver plate, described driver plate respectively with the other end of described first drive link
It is rotationally connected with the other end of described second drive link, and described driver plate is rotationally connected with described fuselage；
Make described steering wheel to the active force of described second drive link by described driver plate, be transferred to described the
One drive link.
Optionally, described driver plate includes: the first point；Second point；And thirdly；Wherein, described
The other end of the first drive link is rotationally connected at described first with described driver plate so that described
One drive link can rotate relative to described first drive link at described first；Described second transmission
The other end of bar is rotationally connected at described second point with described driver plate so that described second drive link
Can rotate relative to described second drive link at described second point；Described driver plate is thirdly being located
It is rotationally connected with described fuselage, and described driver plate can be carried out by the most described fuselage at described thirdly place
Rotate.
Optionally, described chiller includes: cooler bin；Return duct；Wherein, described cooler bin leads to
Cross described return duct to be connected with described reduction box so that fluid passes through described return duct at described reduction box
And circulate, to increase the described fluid travelling distance in fuselage interior between described cooler bin；And
The peripheral position of described cooler bin and described reduction box is pasted with fin.
Optionally, described fixing device includes: the first sleeve；And fixed plate；Wherein, described first
Sleeve is set on described tail transmission shaft, and described fixed plate is set on described first sleeve, and described
The outside of fixed plate is fixing with described fuselage to be connected, to be incited somebody to action by described first sleeve and described fixed plate
The inside being fixed on described fuselage that described tail transmission shaft is firm, to prevent described tail transmission shaft from jumping
Dynamic.
Optionally, described fixing device also includes: limiting plate, and wherein, described fixed plate offers
One hole, location, the aperture in described first hole, location, more than the excircle diameter of described first sleeve, makes institute
State the first sleeve to be located in described first hole, location；Described limiting plate offers the second hole, location, institute
State the aperture excircle diameter more than described first sleeve in the second hole, location, make described first sleeve wear
It is located in described second hole, location；Described limiting plate is connected by fixing with described fixed plate.
Optional: described return duct includes: the first flexible pipe and the second flexible pipe；Described cooler bin includes
One oil-in and first oil-out corresponding with described first oil-in；Described reduction box includes second
Oil-in and second oil-out corresponding with described second oil-in；Wherein, described first oil-in
Connected with described second oil-out by described first flexible pipe；Described first oil-out passes through described second
Flexible pipe connects with described second oil-in.
Optional: described fin is aluminium flake.
The application has the beneficial effect that:
(1) the application use described first bar and described second bar by socket, and described first bar and institute
State and be provided with elastic ball between the second bar, it is ensured that the reliability and stability of connection, on the one hand improve
The shock resistance of described support component, on the other hand, adds the cushion effect after member stress, it is to avoid described
Support component, by crossing large impact, improves the life-span of described support component, the final final drive shaft realized
Safety and firmness run.
(2) the application is by arranging the first drive link, the second drive link and driver plate, by steering wheel and
Two drive links connect, and the second drive link is connected with driver plate, and driver plate and the first drive link connect, so
Steering wheel acts on the power of the second drive link, passes sequentially through driver plate, the first drive link is ultimately applied to main rotation
The wing so that be made up of primary transmission the first drive link, the second drive link and driver plate to amplify described steering wheel
Thrust, decrease the loss of energy.
(3) the application is by setting up cooler bin and return duct so that be in the oil of reduction box in fuselage interior
Liquid, is circulated in cooler bin and reduction box by return duct, increases the fluid trip in fuselage interior
Dynamic distance, meanwhile, is provided with fin at the peripheral position of reduction box and cooler bin, with to reduction box
Dispel the heat further with cooler bin, solve in prior art cooling type unmanned aerial vehicle body internal heat dissipating effect not
Good technological deficiency.
(4) the application sets up the first sleeve and fixed plate by setting, and first set jacket casing is located at tail transmission shaft
Outside, fixed plate is set in the outside of the first sleeve so that by tail transmission shaft and the fuselage of fuselage interior
It is relatively fixed, is effectively prevented cooling type unmanned plane and leads owing to tail transmission shaft is long in flight course
The technological deficiency easily beated caused.
Accompanying drawing explanation
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will
In describing embodiment, the required accompanying drawing used is briefly described, it should be apparent that, in describing below
Accompanying drawing be only embodiments more of the present utility model.
Fig. 1 is in the application one better embodiment, cooling type unmanned plane structural representation；
Fig. 2 is in the another better embodiment of the application, the structural representation of cooling type unmanned plane；
Fig. 3 is the structural representation of fixing device in Fig. 1；
Fig. 4 is the structural representation of the application chiller；
Fig. 5 is the structural representation of the application reduction box；
Fig. 6 is the partial view of a support component in Fig. 2；
Fig. 7 be in Fig. 1 brake wheel structural representation；
Fig. 8 is the right view of brake wheel in Fig. 7.
Detailed description of the invention
In order to be better understood from technique scheme, below in conjunction with Figure of description and concrete enforcement
Technique scheme is described in detail by mode.
Refer to Fig. 1 and Fig. 2, a kind of cooling type unmanned plane 100 that the application provides, described cooling type
Unmanned plane at least includes that fuselage 1, main rotor 2, tail rotor 3 and electromotor 4, described main rotor 2 revolve
Turning to provide lifting force, described tail rotor 3 rotates to offset the torsion produced when described main rotor 2 rotates
Square, to ensure the smooth flight of described cooling type unmanned plane 100.
Concrete, referring to Fig. 3, tail transmission shaft 7 is for being transferred to by the driving force of electromotor 4
Tail rotor 3.Due to distant apart from described electromotor 4 of described tail rotor 3, described tail transmission
Axle 7 easily produces in-flight at cooling type unmanned plane 100 beats.And the fixing device that the application provides
Tail transmission shaft 7 is connected by 8 with fuselage 1, with fixing tail transmission shaft 7, reduces described tail transmission shaft 7
Amplitude of beating.Described fixing device 8 includes the first sleeve 82, fixed plate 81 and limiting plate 83,
Described first sleeve 82 is set on described tail transmission shaft 7, and the outside of described fixed plate 81 is with described
Fuselage 1 is fixing to be connected, and described fixed plate 81 offers the first hole, location, the hole in described first hole, location
Footpath, more than the excircle diameter of described first sleeve 82, makes described first sleeve 82 be located in described the
In one hole, location.Described limiting plate 83 offers the second hole, location, and the aperture in described second hole, location is big
In the excircle diameter of described first sleeve 82, described first sleeve 82 is made to be located in described second fixed
In hole, position.Described limiting plate 83 is bolted with described fixed plate 81, and by bolt with
It is provided with surplus between screwed hole, reduces beating of tail transmission shaft 7, and be hardly damaged described tail transmission
Axle 7.Concrete, described limiting plate 83 and described fixed plate 81 all offer screwed hole, and adopts
It is located in described screwed hole with the bolt leaving surplus with described screwed hole with fixing described fixed plate
81 and described limiting plate 83, reduce beating of described tail transmission shaft 7, and be hardly damaged described tail and pass
Moving axis 7.By arranging the first sleeve 82, described first sleeve 82 is set in described tail transmission shaft 7
In, to avoid described tail transmission shaft 7 and described limiting plate 83 or the direct friction of described fixed plate 81
And wear and tear, improve the life-span of described tail transmission shaft 7.
Further, incorporated by reference to Fig. 1-2 in the lump refering to 4-5, the embodiment of the present application additionally provides one
Chiller.Reduction box 12 is connected with described electromotor 4, for the power to the output of described electromotor 4
Carry out regulator drive.Described chiller includes that at least one cooler bin 13, described cooler bin 13 wrap
Include the first oil-in and first oil-out corresponding with described first oil-in；Described reduction box 12
Including the second oil-in and second oil-out corresponding with described second oil-in；Described first oil-feed
Mouth connects with described second oil-out, it is preferred that described first oil-in leads to described second oil-out
Cross first hose connection and connect；Described first oil-out connects with described second oil-in, it is preferred that
Described first oil-out and described second oil-in are hose connection and connect by second.And the application is logical
Cross a sheathed worm structure on the gear shaft in described reduction box 12 so that described worm structure rotates
Time the gear oil in described reduction box 12 is pressed onto in described cooler bin 13, make described cooling type unmanned
The fuselage interior structure cooling of machine 100 is more abundant.Certainly, reduction box 12 and cooler bin in the application
The peripheral position of 13 is also respectively provided with fin, to strengthen radiating effect further.As preferably,
This fin can be aluminium flake.
Based on same utility model design, the application is at the tail rotor of described cooling type unmanned plane 100
It is also equipped with a chiller at the reduction box 12 that 3 structure divisions are arranged, common is applied to cooling type
The chiller 100 of unmanned plane cools down the Local cooling being the most all to use, by adding gear oil, and
The gear-box surface being applied to reduction box 12 in the chiller 100 of cooling type unmanned plane described in dependence is entered
Row heat radiation, the heat radiation of this type of cooling is slow, and is only capable of the described cooling being applied to cooling type unmanned plane
Dispelling the heat in local in device 100, can not obtain good radiating effect.The application provides
The chiller 100 being applied to cooling type unmanned plane also includes afterbody reduction box 12 and chiller.Tool
Body, described reduction box 12 is connected with described electromotor 4, for the power to the output of described electromotor 4
Carry out regulator drive.The described chiller 100 being applied to cooling type unmanned plane also includes at least one
Cooler bin 13, described cooler bin 13 includes the first oil-in and corresponding with described first oil-in
First oil-out；Described reduction box 12 includes the second oil-in and corresponding with described second oil-in
Second oil-out；Described first oil-in connects with described second oil-out, it is preferred that described first
Oil-in passes through hose connection with described second oil-out and connects；Described first oil-out and described the
Two oil-in connections, it is preferred that described first oil-out and described second oil-in are by hose connection
And connect.And the application is by a sheathed worm structure on the gear shaft in described reduction box 12, makes
Obtain when described worm structure rotates and the gear oil in described reduction box 12 be pressed onto in described cooler bin 13,
The fuselage interior structure cooling making cooling type unmanned plane 100 is more abundant.
Further, please continue to refer to Fig. 4, present invention also provides a kind of thrust amplifying mechanism 9, with
Steering wheel connects；Described steering wheel is used for controlling cooling type unmanned plane 100 flight attitude and track.Described push away
Force amplificatory structure 9 increases the thrust that the transmission of one-level and described steering wheel produces with amplification steering wheel, reduces energy
Amount loss.Concrete, described thrust amplifying mechanism 9 includes first drive link the 91, second drive link 93
And driver plate 92, described driver plate 92 includes 1: 921, second point 923 and thirdly 922.
Described driver plate 92 is connected with described first drive link 91 and described second drive link 93 respectively；Described
One end of first drive link 91 is force side, one end of described first drive link 91 and described fuselage 1
Fixing connection, the other end of described first drive link 91 and described driver plate 92 are described 1: 921
Place is fixing to be connected, and described first drive link 91 can rotate relative to described 1: 921.Described second
One end of drive link 93 is fixing at described second point 923 with described driver plate 92 to be connected, and described
Second drive link 93 can rotate relative to described second point 923, the other end of described second drive link 93
It is connected with described steering wheel.Described driver plate 92 is connected with described fuselage 1 at thirdly 922, and institute
State driver plate 92 can relative to described in thirdly 922 rotate.By arranging the first drive link 91, second
Drive link 93 and driver plate 92 increase primary transmission to amplify the thrust of described steering wheel, reduce energy and damage
Consumption.
Preferably, described first drive link 91 and described driver plate 92 are hinged at 1: 921；
Described second drive link 93 and described driver plate 92 are hinged at second point 923；Described driver plate 92
With described fuselage 1 at thirdly 922 hinged.
Preferably, described 1: 921, second point 923 and thirdly 922 position triangular in shape.
Further, refer to Fig. 6, present invention also provides a kind of support component 11, be applied to cold
But type unmanned plane 100, the support component 11 that the application provides is arranged in described fuselage 1, for propping up
Support and the spacing collar of fixing described final drive shaft 10.Described support component 11 is by using 3
Support, supporting construction is stablized and to the work that can play damping in described cooling type unmanned plane 100 flight course
With.Concrete, described support component 11 includes the first bar the 111, second bar 113 and positioning seat 114；
One end of described first bar 111 is removably secured with described fuselage 1 and is connected, described first bar 111
The other end offer a groove；One end of described second bar 113 is set in described groove, described
Put in the end of one end of the second bar 113 and the inwall of described groove and be provided with one or more elastic ball
112 so that the stress between described first bar 111 and described second bar 113 is buffered, reduce shake
Dynamic.
In the present embodiment, described elastic ball 112 is baton round；Another of described second bar 113
End is provided with the first lug, and described first lug offers the first through hole, the one of described positioning seat 114
End is provided with the second lug, and described second lug offers the second through hole mated with described first through hole,
Described first through hole is bolted with described second through hole, makes described second bar 113 energy institute relatively
State positioning seat 114 to rotate.In order to reduce the vibrations of described support component 11, described positioning seat further
The other end of 114 is also arranged with a resilient sleeve, and described resilient sleeve is I-shaped, described resilient sleeve
It is set on described positioning seat 114, and the groove of the I-shaped of described resilient sleeve is fastened on described
On the fuselage 1 of cooling type unmanned plane 100, so that described positioning seat 114 is fixing even with described fuselage 1
Connect.
In the present embodiment, described resilient sleeve is rubber sleeve.Improve further by arranging resilient sleeve
The shock resistance of a support component 11 described in.Described first bar 111 passes through socket with described second bar 113,
And it is provided with elastic ball 112 between described first bar 111 and described second bar 113, also improve institute
State the shock resistance of a support component 11.The application uses described first bar 111 and described second bar 113
By socket, and it is provided with elastic ball 112 between described first bar 111 and described second bar 113,
Instead of the hinged etc. of routine, described first bar 111 and described second bar 113 are ensured by pretightning force
The reliability and stability connected, on the one hand improves the shock resistance of described support component 11, another
Aspect, adds the cushion effect after member stress, it is to avoid described support component 11 by crossing large impact,
Improve the life-span of described support component 11.
Further, incorporated by reference to Fig. 1-2 in the lump refering to Fig. 7-8, the present embodiment additionally provides one and rises and falls
Device, for take-off and landing device, including a undercarriage 5 and brake wheel 6, described undercarriage 5 is solid
Surely the bottom of described fuselage 1 it is arranged on.Described brake wheel 6 is removably secured with described undercarriage 5
Connect.Being provided for reducing described in when described cooling type unmanned plane 100 rises and falls of described brake wheel 6 is risen
Fall the abrasion of frame 5, and described brake wheel 6 is manually controllable, simple in construction and convenient dismounting.
Concrete, described undercarriage 5 offers the first fixing hole, described first fixing hole for
Described brake wheel 6 with the use of, to be plugged in described first fixing hole and described brake by fixture
In wheel 6, make described brake wheel 6 fix with described undercarriage 5 and be connected.In the present embodiment, institute
State fixture and be specially latch.
Further, described brake wheel 6 includes rotating wheel 61, connecting plate 62 and controlling bar 63.Institute
State rotation wheel 61 and include that a rotary shaft, described rotation wheel 61 can be revolved around the centrage of described rotary shaft
Turn.One end of described connecting plate 62 is fixing with described rotary shaft to be connected；Control bar, with described connecting plate
The other end of 62 is removably secured connection；Described control bar 63 moves up or down, and makes described
Connecting plate 62 rotates and regulates the described height rotating wheel 61.Concrete, the one of described connecting plate 62
End offers the first connecting hole, and the other end of described connecting plate 62 offers the second connecting hole, described company
Being further opened with the second fixing hole on fishplate bar 62, described second fixed hole position is in described first connecting hole and institute
State between the second connecting hole.Described control bar 63 is removably secured with described connecting plate 62 and is connected,
Preferably, one end of described control bar 63 is provided with a fixed part, and described fixed part is located in described
In two connecting holes, and it is connected by latch or clip are fixing with described connecting plate 62.Described rotary shaft is worn
Being located in described first connecting hole, described rotary shaft is at described first connection hole and described connecting plate 62
Fixing connection so that rotate the height of wheel 61 when described connecting plate 62 rotates described in adjustable.This Shen
Connecting plate 62, rotary shaft and control bar 63 please be use to form a linkage, and combine control bar 63
The position of mobile adjustment brake wheel 6, simple in construction and convenient dismounting.
During operation, manually make described control bar 63 move up or down, make described rotation wheel 61
Move down, when the described minimum altitude minimum altitude less than described undercarriage 5 rotating wheel 61, and
The difference in height of the described minimum altitude and the minimum altitude of described undercarriage 5 rotating wheel 61 equals to or more than
During preset value, in described first fixing hole and described second fixing hole, plug fixture, with fixing institute
State brake wheel 6.The brake wheel 6 that the application is arranged, Non-follow control and readily accessible, reduce described rising
Fall the abrasion of frame 5, improves the life-span of described cooling type unmanned plane 100.
The application has the beneficial effect that:
1, the application by arrange brake wheel reduce when described cooling type unmanned plane rises and falls described in rise and fall
The abrasion of frame, and described brake wheel is manually controllable, simple in construction and convenient dismounting.
2, the application use described first bar and described second bar by socket, and described first bar and institute
State and be provided with elastic ball between the second bar, it is ensured that the reliability and stability of connection, on the one hand improve
Described in, the shock resistance of a support component, on the other hand, adds the cushion effect after member stress, it is to avoid institute
State support component by crossing large impact, improve the life-span of described support component, the final main transmission realized
The safety and firmness of axle runs.
3, the application is by arranging the first drive link, the second drive link and driver plate, by steering wheel with
Second drive link connects, and the second drive link is connected with driver plate, and driver plate and the first drive link connect,
So steering wheel acts on the power of the second drive link, passes sequentially through driver plate, the first drive link finally acts on
In main rotor so that constituted primary transmission by the first drive link, the second drive link and driver plate and amplify
The thrust of described steering wheel, decreases the loss of energy.
4, the application is by setting up cooler bin and return duct so that be in the oil of reduction box in fuselage interior
Liquid, is circulated in cooler bin and reduction box by return duct, increases the fluid trip in fuselage interior
Dynamic distance, meanwhile, is provided with fin at the peripheral position of reduction box and cooler bin, with to reduction box
Dispel the heat further with cooler bin, solve cooling type unmanned aerial vehicle body internal heat dissipating effect in prior art
Bad technological deficiency.
5, the application sets up the first sleeve and fixed plate by setting, and first set jacket casing is located at tail transmission
The outside of axle, fixed plate is set in the outside of the first sleeve so that by the tail transmission shaft of fuselage interior with
Fuselage is relatively fixed, and is effectively prevented cooling type unmanned plane in flight course due to tail transmission shaft mistake
The technological deficiency easily beated grown and cause.
It should be noted last that, above detailed description of the invention is only in order to illustrate technology of the present utility model
Scheme and unrestricted, although this utility model being described in detail with reference to example, this area general
Logical it will be appreciated by the skilled person that the technical solution of the utility model can be modified or be equal to and replace
Changing, without deviating from the spirit and scope of technical solutions of the utility model, it all should contain in this practicality new
In the middle of the right of type.
Claims (10)
1. a cooling type unmanned plane, including fuselage, main rotor, tail rotor, steering wheel, electromotor and
Reduction box, described reduction box is connected with described electromotor, and wherein, described main rotor passes through final drive shaft
It is rotatably fixed with described fuselage and is connected；Described tail rotor is fixedly installed on the afterbody of described fuselage,
And be rotatably fixed with described fuselage by tail transmission shaft and to be connected；Described electromotor and described main rotor
Connecting with described tail rotor, be used for driving described main rotor and described tail rotor to rotate, described steering wheel is solid
Inside due to described fuselage；It is characterized in that, described cooling type unmanned plane also includes:
Propping up support component, described support component is arranged in described fuselage, is used for supporting and fix described master
Power transmission shaft；
Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify described steering wheel
The thrust produced；
Chiller, described chiller is connected with described reduction box；
Fixing device, described fixing device is set on described tail transmission shaft, and fixes with described fuselage
Connect, so that described tail transmission shaft and described fuselage are relatively fixed.
2. cooling type unmanned plane as claimed in claim 1, it is characterised in that described support component bag
Include:
First bar；
Second bar；And
Positioning seat；Wherein, one end of described first bar is removably secured with described final drive shaft and is connected,
The other end of described first bar offers a groove；One end of described second bar is set in described groove,
The end of one end of described second bar, with the inwall of described groove, is put and is provided with one or more elastic ball,
Stress between described first bar and described second bar is buffered；The other end of described second bar
It is rotationally connected with one end of described positioning seat so that described second bar is rotatable relative to described positioning seat.
3. cooling type unmanned plane as claimed in claim 2, it is characterised in that:
The other end of described positioning seat is by flexible being fixed on described fuselage of a resilient sleeve, so that institute
State positioning seat to flexibly connect with described fuselage.
4. cooling type unmanned plane as claimed in claim 1, it is characterised in that described thrust enlarger
Structure includes:
First drive link, one end of described first drive link is fixed on described fuselage；
Second drive link, one end of described second drive link is fixed on the steering wheel of described fuselage interior；
And
Driver plate, described driver plate respectively with the other end of described first drive link and described second transmission
The other end of bar is rotationally connected, and described driver plate is rotationally connected with described fuselage；Make described steering wheel
The active force of described second drive link is passed through described driver plate, is transferred to described first drive link.
5. cooling type unmanned plane as claimed in claim 4, it is characterised in that described driver plate includes:
First point；
Second point；And
Thirdly；Wherein, the other end of described first drive link and described driver plate are at described first point
Place is rotationally connected so that described first drive link can the most described first drive link at described first
Rotate；The other end of described second drive link and described driver plate company of rotation at described second point
Connect so that described second drive link can rotate relative to described second drive link at described second point；
Described driver plate thirdly place be rotationally connected with described fuselage, and described driver plate described thirdly
Place can rotate relative to described fuselage.
6. cooling type unmanned plane as claimed in claim 1, it is characterised in that described chiller bag
Include:
Cooler bin；
Return duct；
Wherein, described cooler bin is connected with described reduction box by described return duct so that fluid passes through
Described return duct circulates between described reduction box and described cooler bin, exists increasing described fluid
The travelling distance of fuselage interior；And the peripheral position of described cooler bin and described reduction box is pasted with heat radiation
Sheet.
7. cooling type unmanned plane as claimed in claim 6, it is characterised in that:
Described return duct includes: the first flexible pipe and the second flexible pipe；
Described cooler bin includes the first oil-in and corresponding with described first oil-in first fuel-displaced
Mouthful；
Described reduction box includes the second oil-in and corresponding with described second oil-in second fuel-displaced
Mouthful；
Wherein, described first oil-in is connected with described second oil-out by described first flexible pipe；Institute
State the first oil-out to be connected with described second oil-in by described second flexible pipe.
8. cooling type unmanned plane as claimed in claim 6, it is characterised in that:
Described fin is aluminium flake.
9. cooling type unmanned plane as claimed in claim 1, it is characterised in that described fixing device bag
Include:
First sleeve；And
Fixed plate；Wherein, described first set jacket casing is located on described tail transmission shaft, described fixing sleeve-board
It is located on described first sleeve, and the outside of described fixed plate is fixed with described fuselage and is connected, to pass through
Described first sleeve and described fixed plate are by firm being fixed in described fuselage of described tail transmission shaft
Portion, to prevent described tail transmission shaft from beating.
10. cooling type unmanned plane as claimed in claim 9, it is characterised in that described fixing device
Also include:
Limiting plate, wherein,
Described fixed plate offers the first hole, location, and the aperture in described first hole, location is more than described first
The excircle diameter of sleeve, makes described first sleeve be located in described first hole, location；
Described limiting plate offers the second hole, location, and the aperture in described second hole, location is more than described first
The excircle diameter of sleeve, makes described first sleeve be located in described second hole, location；
Described limiting plate is connected by fixing with described fixed plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620283256.2U CN205652347U (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620283256.2U CN205652347U (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN205652347U true CN205652347U (en) | 2016-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201620283256.2U Withdrawn - After Issue CN205652347U (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN205652347U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864758A (en) * | 2017-03-02 | 2017-06-20 | 西安天问智能科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle engine damping of oil |
| CN105836116B (en) * | 2016-04-07 | 2019-02-19 | 易瓦特科技股份公司 | Cooling type unmanned plane |
-
2016
- 2016-04-07 CN CN201620283256.2U patent/CN205652347U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105836116B (en) * | 2016-04-07 | 2019-02-19 | 易瓦特科技股份公司 | Cooling type unmanned plane |
| CN106864758A (en) * | 2017-03-02 | 2017-06-20 | 西安天问智能科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle engine damping of oil |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161019 Effective date of abandoning: 20190219 |